Fastener cover for flowpath fasteners
AssigneeGeneral Electric Company
InventorsRicha Awasthi, Bhanu Kishore Battu, Viswanadha Gupta Sakala, Michael Jason Bishop
Life of this patent
Estimating the term…
Abstract
A fastener cover assembly is disclosed. The cover assembly includes a turbomachinery component having an outer surface exposed to an air flow path; at least one recess formed in the outer surface; a fastener contained in the at least one recess; and a fastener cover secured in the at least one recess, the cover having an outer surface substantially flush with the outer surface of the component to minimize air flow disruption.
Claims18
A fastener cover assembly, comprising:
- a turbomachinery component having an outer surface exposed to an air flow path;
- at least one recess formed in the outer surface;
- a fastener contained in the at least one recess, wherein a head of the fastener is at a position below the outer surface of turbomachinery component;
- and
- a fastener cover secured in the at least one recess, the cover having an outer surface substantially flush with the outer surface of the turbomachinery component to minimize air flow disruption, wherein at least a portion of the fastener cover resides between the head of the fastener and the outer surface of the turbomachinery component.
A spinner assembly for a gas turbine engine, comprising:
- a spinner having an outer surface exposed to an air flow path, the spinner including at least one recess formed in the outer surface;
- a fastener secured in the at least one recess, wherein a head of the fastener is at a position below the outer surface of the spinner;
- and
- a fastener cover secured in the at least one recess, the cover having an outer surface substantially flush with the outer surface of the spinner to minimize air flow disruption and includes:
- an end wall;
- a cavity configured to secure the head of the fastener therein;
- an aperture extending through the fastener cover from the outer surface of the fastener cover to the cavity, wherein the cavity is positioned between the aperture and the end wall;
- and
- wherein the end wall includes an opening configured to receive a shank of the fastener therethrough when the head is secured in the cavity.
A spinner assembly for a gas turbine engine, comprising:
- a spinner having an outer surface exposed to an air flow path, the spinner including at least one recess formed in the outer surface;
- a fastener secured in the at least one recess, wherein a head of the fastener is at a position below the outer surface of the spinner;
- and
- a fastener cover secured in the at least one recess, the cover having an outer surface substantially flush with the outer surface of the spinner to minimize air flow disruption and includes:
- an end wall having a recess formed therein, the recess configured to slip over the head of the fastener;
- an aperture extending through the fastener cover from the outer surface to a divider wall separating the aperture and the recess, the divider wall having an aperture extending therethrough;
- and
- a second fastener extending through the aperture in the divider wall and into a threaded aperture in the head of the fastener to secure the fastener cover to the fastener.
Dependencies are inferred from the claim text.